US4151968A - Night guiding device for self-propelled missiles - Google Patents

Night guiding device for self-propelled missiles Download PDF

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Publication number
US4151968A
US4151968A US05/745,225 US74522576A US4151968A US 4151968 A US4151968 A US 4151968A US 74522576 A US74522576 A US 74522576A US 4151968 A US4151968 A US 4151968A
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Prior art keywords
detectors
telescope
signals
pulse
filter
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US05/745,225
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English (en)
Inventor
Pierre M. L. Lamelot
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Societe Anonyme de Telecommunications SAT
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Societe Anonyme de Telecommunications SAT
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Priority claimed from FR7536722A external-priority patent/FR2334079A1/fr
Priority claimed from FR7619495A external-priority patent/FR2356115A2/fr
Priority claimed from FR7621338A external-priority patent/FR2358633A2/fr
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
    • G01S3/78—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using electromagnetic waves other than radio waves
    • G01S3/782—Systems for determining direction or deviation from predetermined direction
    • G01S3/789—Systems for determining direction or deviation from predetermined direction using rotating or oscillating beam systems, e.g. using mirrors, prisms
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41G—WEAPON SIGHTS; AIMING
    • F41G7/00—Direction control systems for self-propelled missiles
    • F41G7/20—Direction control systems for self-propelled missiles based on continuous observation of target position
    • F41G7/30—Command link guidance systems
    • F41G7/301—Details
    • F41G7/303—Sighting or tracking devices especially provided for simultaneous observation of the target and of the missile
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
    • G01S3/78—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using electromagnetic waves other than radio waves

Definitions

  • the present invention relates to the night guidance of missiles, more particularly self-propelled missiles guided from a remote-control station towards a mobile or stationary target.
  • Daylight guidance of such missiles is well known. It is an indirect guidance achieved by alignment on an axis optically defined by the reticle of a sighting telescope having its crossing point maintained by the observer sitting in the control station in coincidence with the target.
  • the angular deviations of the missile in relation to the optical axis thus defined are delivered to the observer by means of an infrared goniometric optical device detecting the infrared source, called "tracer", carried by the missile, the unit formed by the daylight sighting telescope and the infrared goniometer being called infrared localizing apparatus.
  • the daylight guiding system is designed in such manner that the distance between the optical axes of the sighting telescope and of the goniometer is small compared to the guiding accuracy desired, i.e. less than 0,1 mrd.
  • the goniometer optical axis forms with the lign of sight an angle which is smaller than 0,1 mrd due to an appropriate mechanical coupling and an optical adjustment made in the factory.
  • a night observation system of the thermal imagery type having an optical axis also defined by the crossing point of a reticle.
  • the guidance of the missile is achieved as soon as the thermal telescope optical axis coincides with the goniometer optical axis.
  • a thermal telescope comprises for instance a linear array of infrared elementary detectors, called bar of infrared elementary detectors, associated with a mechanical scanning device along one or two rectangular axes, or also a matrix array of elementary detectors.
  • the mechanical assembly techniques do not ensure without adjustment the coincidence of the optical axis of such a night telescope with the goniometer optical axis; the initial adjustment could also be unstable due to the resilience of the mechanical links.
  • the included angle between these axes represents the mechanical adjustment accuracy of such a night telescope.
  • the object of the invention is to reduce the observed value of this angle to zero, that is, to achieve coincidence of the optical axis of the thermal telescope with the optical axes of both the daylight sighting telescope and the goniometer to which the former is rigidly connected, the coincidence being automatically achieved after the departure of the missile.
  • a device comprising a daylight sighting telescope and an infrared goniometer, the unit being called localizing apparatus, for detecting a missile-born infrared source, and a night vision termal telescope, said device further comprising a computer receiving through storage, amplifying and processing means, on the one hand the signals provided by the localizing apparatus and characteristic of the missile position in relation to the optical axis of said localizing apparatus, and on the other hand the signals provided by the thermal telescope and characteristic of the missile position in relation to the optical axis of said thermal telescope, said computer supplying to a visualization device associated with said thermal telescope signals representative of the difference between the signals received respectively from the localizing apparatus and the thermal telescope.
  • the pyrotechnical missile-borne tracer is not an infrared radiation transmitter sufficiently contrasty to be tracked with the required accuracy.
  • the thermal telescope provided with a focusing lens and a scanning device along one direction incorporates a detecting device comprising two infrared detectors, the first being responsive to the transmitting spectral range of the target and landscape and the second being responsive to the transmitting spectral range of the missile-borne tracer.
  • Both detectors may be formed each with a linear array of elementary detectors arranged transversely to the scanning direction, both arrays being located in the thermal telescope focus plane.
  • the first detector is a linear array of elementary detectors arranged transversely to the scanning direction
  • the second detector comprises two threadlike detectors non-parallel to the scanning direction and non-parallel between themselves. Both threadlike detectors being non-parallel, the two pulses which they deliver will be separated by a time interal depending on the co-ordinate Y of the tracer image along axis Y'-Y perpendicular to the scanning direction.
  • these two pulses allow in connection with reference pulses generated by the scanning device the coordinates X, Y to be determined by a very simple electronic processing.
  • the detecting device comprises a single infrared detector particularly responsive to the transmitting spectral range of the target and landscape, and sufficiently responsive to the transmitting spectral range of the tracer to track it, a first optical filter defining a wide wave-length band for detecting the target and landscape, a second optical filter defining a very narrow band for detecting the tracer, and a selection member for placing either the first filter or the second filter on the telescope optical axis.
  • the aforesaid selection device When it is desired to track the missile, the aforesaid selection device is tilted, said device being for instance a disc eccentric in relation to the telescope optical axis and provided with two openings accommodating the filters, in the position where the second filter is on the telescope optical axis.
  • a well contrasty image of the tracer is thus obtained since in the very narrow band defined by the second filter, the energy radiated by the target and landscape is negligible while the transmitted fraction of the tracer radiation is sufficient to allow detection.
  • FIG. 1 shows the relative positions of the optical axes of the three view-finders available to the observer
  • FIG. 2 is a block-diagram of the thermal telescope according to the invention provided with a detecting device of a first type;
  • FIG. 3 is a front view of the detectors of the telescope of FIG. 2 in a first embodiment
  • FIG. 4 shows the relative positions of the three reticles of the view-finders before coincidence of their optical axes is achieved
  • FIGS. 5 and 6 show alternative embodiments of the detectors of FIG. 2;
  • FIG. 7 shows a thermal telescope provided with a second type of detecting device
  • FIG. 8 shows an embodiment of the detector for tracking the missile-borne tracer
  • FIG. 9 is an analog processing circuit diagram for determining the co-ordinates of the tracer
  • FIG. 10 is a time chart illustrating the processing performed by the circuit of FIG. 9;
  • FIG. 11 is a digital processing circuit diagram for determining the co-ordinates of the tracer
  • FIG. 12 is a time chart illustrating the processing performed by the circuit of FIG. 11;
  • FIG. 13 shows a thermal telescope provided with a third type of detecting device
  • FIG. 14 shows the response of the detector used in the described embodiment, the atmospheric windows being hatched.
  • FIGS. 15 and 16 show the transmitting curves of the target and environing landscape, and the tracer, respectively, the atmospheric windows being also shown by the hatched areas.
  • a bar of elementary detectors for instance of Cd x HG 1-x Te, whose sensitivity is centered on the spectral area 3 ⁇ to 5 ⁇ , or 8 ⁇ to 12 ⁇ is placed in the focal plane of lens 1 of the thermal telescope which forms the night sighting system.
  • the bar may be replaced by a mosaic array of elementary detectors of same sensitivity corresponding to the infrared transmitting range of a target B and its environment.
  • a mosaic array 4 of detectors or also a second bar 4 of infrared detectors with sensitivity centered on wave-lengths, 1,5 to 2,5 ⁇ , area in which the radiation of the missile-borne tracer B presents a maximum contrast are placed in the same focal plane of lens 1.
  • Both detectors 3 and 4, or arrays of detectors may be associated in various ways as will be described later. They may be placed side by side (FIG. 3), or superimposed (FIG. 5) or displaced in the same focal plane (FIG. 6).
  • lens focal plane is only an approximation in the case where the optics of the telescope are not achromatic, which is the case of a lens, since the focal distance varies then slightly in relation to the radiation wave-length to be detected.
  • a horizontal scanning device 2 along O'X is arranged in front of detectors 3 and 4 to scan the night field of vision in the case where detectors 3 and 4 are simple bars.
  • the scanning device 2 can be a plane mirror to which a motor imparts an oscillating movement. It moves then about an axis parallel to the direction O'Y defined by the detecting bars.
  • the scanning device 2 may also be formed by a straight prism rotating about an axis parallel to O'Y. Any other scanning device may supply a field of vision along direction O'X by means of the same detecting bar.
  • the device 2 could also be placed in front of lens 1.
  • a bar of elementary detectors 4, sensitive to the 1,5 to 2,5 ⁇ wave-length radiation has been placed side by side in the vicinity of the center of the bar 3, on the same substrate.
  • Angle ⁇ of FIG. 1, i.e. the initial angular distance between the optical axes, is small enough to permit using a bar formed of only sixteen elementary detectors in form of small squares of 0,12 mrd sides placed two by two on the side of each elementary detector of the first bar 3.
  • FIG. 3 brings precisions as to how the two bars are arranged.
  • the detection of the missile in the center of the night field of vision is achieved while forming an image made of two interlaced frames of sixteen scanning lines in a 4 mrd area at O'Y and a 25 mrd area at O'X.
  • the bar 4 made of sixteen elements sensitive from 1,5 ⁇ to 2,5 ⁇ delivers the angular deviations of the missile-borne tracer in the vicinity of the center of the night field of vision with a precision at X and Y of the order of 0,06 mrd, since it is possible to distinguish two elements distant of 0,12 mrd.
  • Bar 4 may be made with detectors of for instance Cd x Hg 1-x Te, InAs or PbS.
  • FIG. 4 shows the detection of missile (P) by means of various reticles before achieving the axis coincidence procedure according to the invention.
  • Values (x 2 , y 2 ) are detected at a given moment t o subsequent to the departure of the missile, but this time is chosen brief. This time t o corresponds for instance to a distance covered by the missile of the order of 200 meters. According to FIG. 2, these values are transmitted to the electronic device 5 for storing, amplifying and processing signals, adapted to the detectors used. Finally, the values (x 2 , y 2 ) thus processed are stored for calculations in device 6 as follows:
  • (x 1 , y 1 ) are the missile co-ordinates delivered by the goniometer and therefore measured in relation to the goniometer reticle (L) (see FIG. 4). Values (x 1 , y 1 ) have been detected at the same moment t o as values (x 2 , y 2 ) and supplied to the computer through an electronic storing, amplifying and processing device 7.
  • Device 6 delivers thereafter the corrections (x, y) to the deflection coils or plates of a cathodic tube 8 in the form of electric voltages.
  • the night sighting axis is materialized by a reticle bound for instance to the center of the screen of the sighting cathodic tube 8, observed through an eye-piece.
  • the night sighting device is therefore able to supply the angular deviations of the missile in relation to the crossing point of a night sighting reticle with an accuracy superior to 0,1 mrd.
  • FIGS. 2 and 3 relate to the case where two detectors 3 and 4 are placed side by side. The moments for detecting the field and the missile are then shifted by a known time lapse due to the small distance between the two bars 3 and 4. It is also possible to superimpose detectors 3 and 4 as shown in FIG. 5, by providing a first optical window transparent to the radiation of 3 ⁇ to 5 ⁇ , or 8 ⁇ to 12 ⁇ wave-lengths, said window having itself a sensitivity centered on the window of 1,5 ⁇ to 2,5 ⁇ . Those detectors 3 and 4 analyze the same field at each moment by means of a unique concentration 1 and scanning 2 system shown in FIG. 2, both detectors being attached to the same substrate and eventually inserted in the same cryostat.
  • the purpose of the linear mosaic array 3 is to detect the target which the missile has to reach and also the environing landscape, and to this effect its sensitivity is maximum in the wave-length range of 8 to 12 ⁇ m.
  • Detectors are for instance of Cd x Hg 1-x Te, the value of x being suitably chosen.
  • the threadlike detectors 21 and 22 for localizing the missile-borne tracer have a good sensitivity in the transmitting range of the tracer.
  • Detectors of Cd x Hg 1-x Te for instance are used, in front of which filters (not represented) have been placed to define a narrow wave-length band, for instance 3,8-4 ⁇ m.
  • mosaic array 3 and detectors 21 and 22 are placed in slightly shifted planes, in order to compensate for the chromatic aberration mentionned hereabove due to the use of lenses, for instance made of germanium, for the focusing lens 1.
  • the tracer image is focused exactly in the plane of the threadlike detectors.
  • Detectors 21 and 22 generate respective pulses I 1 and I 2 which are applied to the processing device 5 which will be described hereafter in two different embodiments.
  • Device 5 receives also reference pulses supplied by the scanning device 2 and transmits signals representative of co-ordinates x 2 , y 2 of the tracer in the reference system bound to the thermal telescope.
  • the scanning device delivers a reference pulse a o .
  • a pulse I f is necessary to define the end of a scanning period.
  • the reference pulses a o , I o and I f are supplied directly to the processing device 5 through the electronics associated with the scanning device 2. There is no difficulty in obtaining these pulses from the scanning device for one skilled in the art, and detailed explanations are not necessary.
  • the device comprises four flip-flops 31, 32, 33, 34 to which are respectively applied pulses a o , I 1 , I 2 , I o , as well as pulse I f at the reset input.
  • the corresponding output signals a, b 1 , b 2 and b o are shown in FIG. 4.
  • gate 41 receives signals a and b 1 , gate 41' signals a and b 1 , etc.
  • the output signals of the AND gates are used to control the closing of switches 51, 51', 52, 52', 50 respectively.
  • switches 51 and 52 sets up of a voltage +V
  • the closing of switches 51', 52' and 50 sets up a voltage -V.
  • the polarity of the applied voltage is bound to the sign of t 1 and t 2 . It can be seen that if t 1 is negative, the voltage will be -V (closing of switch 51') and conversely if t 1 is positive, the voltage will be +V (closing of switch 51).
  • rectangular signals T o , T 1 , T 2 are therefore obtained, of duration equal respectively to t 1 , t 2 and t o and with an amplitude of either +V or -V according to the sign of t 1 , t 2 and t o .
  • Resistors 61 and 62 are chosen equal, so that amplifier 60 delivers a signal equal to ##EQU1##
  • Resistors 65, 66, 67, 68 and 69 are chosen so that amplifier 64 transmits a signal equal to ##EQU2##
  • the values of the aforesaid resistors may be chosen freely, and it is only sufficient that they be far greater than the resistances of the aforesaid switches.
  • the instantaneous values of x 2 and y 2 are to be obtained, that is, their values on a single scanning period (interval between two consecutive pulses I f ), it suffices to modify the described circuit by incorporating integrators between the switches and the amplifiers, in order to obtain the average values of T 1 , T 2 , T o on each period, to add a storing capacitor at the output of each amplifier and to suppress filters 70 and 74.
  • the instantaneous values are used for instance when it is requested to record the path of the tracer.
  • FIG. 11 shows another embodiment of the device 5 wherein values x 2 and y 2 are supplied in digital mode.
  • the device comprises four flip-flops 131, 132, 133 and 134 arranged in the same manner as the input flip-flops of the analog device of FIG. 9.
  • the output signals a, b o , b 1 , b 2 shown in FIG. 12 are the same as those of FIG. 10 but shown at a smaller scale for convenience.
  • the aforesaid gates receive signals c, d, e or f coming from the ring counter 145 receiving pulse I f .
  • These signals are rectangular signals with a duration of one scanning period, shifted in relation to one another. The recurrence frequency of these signals is therefore one quarter of the scanning frequency.
  • the up-down counters 150 and 160 are connected respectively to an oscillator 170 transmitting clock impulses. These impulses are counted or deducted only if the up-down counter 150 (or 160) is authorized by the signals from the aforesaid OR gates.
  • Signals C 1 , C 2 which, like signals A 1 , A 2 of the chart of FIG. 10, have “crenels” only if t 1 or t 2 are respectively positive, are applied to the counting input 155 of counter 150. Conversely, signals C' 1 , C' 2 which have “crenels” only if t 1 or t 2 are respectively negative, are applied to the deducting input 156.
  • signal C' 1 authorizes deduction during the first scanning period (crenel of signal c). Of course C 1 is zero since t 1 is negative. During the second period (crenel of signal d), signal C 2 authorized counting.
  • the up-down counter 150 makes the algebrical addition t 1 +t 2 , in other words supplies the co-ordinate x 2 in the form of a number of impulses, and this every four scanning periods.
  • the up-down counter 160 makes similarly the operation t 2 -t 1 -2t o for the calculation of y 2 . It receives C' 1 on its counting input 165 or C 1 on its deducting input 166, during the first scanning period. During the second period, it receives C 2 on its counting input, and C' 2 on its deducting input. Finally, during the third and fourth periods (crenels of signals e and f) it receives signal C o on its deducting input.
  • the up-down counters 150 and 160 thus supply co-ordinates x 2 and y 2 in digital form, which is of interest where a digital computer is to be utilized.
  • the signals representative of co-ordinates x 2 , y 2 are applied to computer 6 as hereabove indicated, with a view to obtain the correction voltages (x, y).
  • FIG. 13 Another embodiment of the thermal telescope is shown on FIG. 13, simplified in comparison to the embodiment of FIG. 2 in that the detecting device comprises a single mosaic array 11 of elementary detectors, for instance of Cd x Hg 1-x Te, formed, as mosaic array 3 of FIG. 2, with a large number of elementary detectors, for instance fifty.
  • the detecting device comprises a single mosaic array 11 of elementary detectors, for instance of Cd x Hg 1-x Te, formed, as mosaic array 3 of FIG. 2, with a large number of elementary detectors, for instance fifty.
  • the response curve of detector 11 is shown in FIG. 14, and it may be seen that the sensitivity is maximum for a wave-length of about 12 ⁇ m, and that it decreases regularly as the wave-length decreases.
  • This shape of the response curve is given only as an example, and it may also be possible to have a maximum sensitivity for another wave-length between 8 and 12 ⁇ m, simply by modifying the proportions of the detector components, that is the value of x.
  • This feature of detector 11 has an advantage in that it allows detection in a very large spectral area. It is clear in particular that a detection remains possible within the atmospheric window around 4 ⁇ m, since the level is still of about 25% of the maximum level.
  • the telescope comprises a disc 12 carrying two filters 13 and 14 mounted in openings.
  • the disc 12 is arranged eccentrically in relation to the optical axis of the telescope in such manner that, according to its angular position, either the filter 13 or the filter 14 is in the optical axis.
  • the disc 12 is connected to an electrically actuated control device 20 owing to which the required filter is placed in the telescope optical axis.
  • Filter 13 is high-pass filter transparent to radiations of a wave-length exceeding 8 ⁇ m.
  • the frequency band which it defines corresponds to the atmospheric window 8-12 ⁇ m.
  • Filter 14 is a low-pass filter defining a very narrow band of 3,8 to 4 ⁇ m, this band being within the atmospheric window around 4 ⁇ m.
  • the transmitting curve of the target and landscape, shown in FIG. 15, and that of the pyrometric missile-borne tracer, shown in FIG. 16, make it clear that filter 13 is used for observing the target and its environment while filter 14 is used for observing the tracer.
  • the transmitted radiation of the target and landscape is intense between 8 and 12 ⁇ m, but weak in the vicinity of 4 ⁇ m, and it can be seen from FIG. 16 that the transmitted radiation of the tracer is maximum around 1,6 ⁇ m, that it is still relatively high around 4 ⁇ m, and that it decreases substantially in the wave-lengths superior to 8 ⁇ m.
  • filter 14 As the band defined by filter 14 is very narrow and as the transmitted radiation of the target and landscape is weak in this wave-length area, a well contrasty image of the tracer will be obtained by using filter 14.
  • Detector 11 is placed in the telescope in such manner as to coincide with the focus of lens 1, for wave-lengths of 8 to 12 ⁇ m corresponding to filter 13.
  • the optics of the telescope schematized by lens 1 are not achromatic, meaning that its focal distance depends on the wave-length of the incoming radiation.
  • the focal distance of a radiation of 3,8-4 ⁇ m wave-length is slightly inferior to the focal distance for a radiation of 8-12 ⁇ m wave-length.
  • Detector 11 being placed in the focal plane corresponding to this wave-length area, that is corresponding to filter 13, a plate with parallel faces 15, for instance made of silicon, whose thickness is calculated in order to obtain focusing in the plane of detector 11, is associated with filter 14 to compensate for the focal distance difference.
  • the mentioned thickness is in practice of 2 to 3 ⁇ m, the refraction index being of 3,4 for silicon.
  • filter 14 is placed on plate 15 as shown in FIG. 1.
  • plate 15 becomes superfluous if achromatic optics are used for the instruments, which should therefore be made of mirrors.
  • the device according to FIG. 13 is identical for the remaining components as the device shown in FIG. 2.
  • disc 12 In order to detect the missile, disc 12 is rotated so as to place filter 14 on the optical axis. This allows co-ordinates x 2 and y 2 of the missile to be determined in the co-ordinate system of the thermal telescope, corresponding to time t o . These co-ordinates are transmitted to the device 5 identical to the device 5 shown in FIG. 2.

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  • Engineering & Computer Science (AREA)
  • Electromagnetism (AREA)
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  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
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  • Combustion & Propulsion (AREA)
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US05/745,225 1975-12-01 1976-11-26 Night guiding device for self-propelled missiles Expired - Lifetime US4151968A (en)

Applications Claiming Priority (6)

Application Number Priority Date Filing Date Title
FR7536722A FR2334079A1 (fr) 1975-12-01 1975-12-01 Dispositif de guidage nocturne d'engins autopropulses
FR7536722 1975-12-01
FR7619495A FR2356115A2 (fr) 1976-06-25 1976-06-25 Dispositif de guidage nocturne d'engins autopropulses
FR7619495 1976-06-25
FR7621338A FR2358633A2 (fr) 1976-07-12 1976-07-12 Dispositif de guidage nocturne d'engins autopropulses
FR7621338 1976-07-12

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USRE33287E (en) * 1980-02-04 1990-08-07 Texas Instruments Incorporated Carrier tracking system
JPH04263800A (ja) * 1990-08-14 1992-09-18 Hughes Aircraft Co 多重ミサイル追跡リンク間の不整列を補正する方法
US5298909A (en) * 1991-12-11 1994-03-29 The Boeing Company Coaxial multiple-mode antenna system
DE3217726C1 (de) * 1981-05-15 2003-07-10 Hughes Aircraft Co Raketenverfolgungsgerät zur Erzeugung von Bahnfehlersignalen

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FR2336655A1 (fr) * 1975-12-22 1977-07-22 Telecommunications Sa Perfectionnement au guidage nocturne d'engins autopropulses
DE2942181C2 (de) * 1979-10-18 1987-11-12 Elektro-Optik GmbH & Co KG, 2392 Glücksburg Optisch-elektronische Anordnung für ein thermografisches Bild- und Trackergerät
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GB2186760B (en) * 1986-02-14 1990-01-04 Philips Electronic Associated Information transmission system

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US3992629A (en) * 1971-03-01 1976-11-16 Hughes Aircraft Company Telescope cluster

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US3352196A (en) * 1963-09-03 1967-11-14 Martin Marietta Corp Sighting device which superimposes the image of target with that of a missile
DE2041530C3 (de) * 1970-08-21 1975-04-03 Messerschmitt-Boelkow-Blohm Gmbh, 8000 Muenchen Verfahren zum Fernlenken eines sich selbsttätig bewegenden Körpers und Einrichtung zur Durchführung des Verfahrens
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US3992629A (en) * 1971-03-01 1976-11-16 Hughes Aircraft Company Telescope cluster
US3796396A (en) * 1971-10-29 1974-03-12 C Crovella Method and apparatus for modulating a pyrotechnic tracer
US3974383A (en) * 1975-02-03 1976-08-10 Hughes Aircraft Company Missile tracking and guidance system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
USRE33287E (en) * 1980-02-04 1990-08-07 Texas Instruments Incorporated Carrier tracking system
DE3217726C1 (de) * 1981-05-15 2003-07-10 Hughes Aircraft Co Raketenverfolgungsgerät zur Erzeugung von Bahnfehlersignalen
JPH04263800A (ja) * 1990-08-14 1992-09-18 Hughes Aircraft Co 多重ミサイル追跡リンク間の不整列を補正する方法
JP2574560B2 (ja) 1990-08-14 1997-01-22 エイチイー・ホールディングス・インコーポレーテッド・ディービーエー・ヒューズ・エレクトロニクス 多重ミサイル追跡リンク間の不整列を補正する方法
US5298909A (en) * 1991-12-11 1994-03-29 The Boeing Company Coaxial multiple-mode antenna system

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Publication number Publication date
DE2654103C2 (de) 1983-11-10
DE2654103A1 (de) 1977-07-07
GB1569306A (en) 1980-06-11

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